叶片弯曲对压气机叶栅气动性能影响的数值模拟  

The numerical simulation of vortices structure in compressor cascade with curved blades

作　　者：王会社[1] 钟兢军[2] 王松涛[2] 王仲奇[2] 袁新[1] 

机构地区：[1]清华大学热能工程系,北京100084 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《空气动力学学报》2002年第4期470-476,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(50076009;50076019);973(G1999022306;G1999022307);全国优秀博士学位论文作者专项基金(199932)资助项目

摘　　要：为了研究压气机中采用弯曲叶片对叶栅流场气动性能的影响,本文应用Beam Warming近似隐式因子分解格式以及MML代数湍流模型,采用拟压缩性方法求解雷诺平均拟压缩N S方程组,对弯曲叶片压气机叶栅内三维粘性流场进行了数值模拟。结果表明,在给定的条件下,三种叶栅内涡系结构具有某种相似性。反弯叶栅吸力面/端壁角区分离严重,中部流动较为理想;正弯叶栅基本消除了吸力面/端壁角区分离,但中部分离较明显;这些又导致三种叶栅流道中涡的大小和强弱存在明显的不同。计算结果与实验结果比较,两者吻合较好。The numerical simulation has been carried out to investigate the secondary flow in the compressor cascades composed of the positive curved blades and negative curved blades.The method of the pseudocompressibility was used and the incompressible NavierStokes equations were solved with BeamWarming's implicit approximate factorization algorithm and the MML turbulence model.It is shown that the structures of vortices in these cascades are similar in some extent under the given condition.Separation is severe in corner area of suction surface/endwall in negative cascade.who has an ideal flow in the midarea,In positive cascade,separation almost disappears in corner of suction surface/endwall,but it appears in the midarea.These result in that the vortices have no the same size and intensity.The agreement of calculated results with the experimental data is favorable.

关 键 词：数值模拟 压气机 弯曲叶片 旋涡 计算流体力学 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]